Composite Hydrogen Tank Joint Reinforcement Against Debonding
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Solution Overview
Problem
Current hydrogen tanks for aircraft face challenges in meeting aircraft-specific debonding requirements, including flight maneuvers, insulation complexity, pressure loads, and bonding failures, which are not adequately addressed by existing technologies.
Innovation Solution
A composite hydrogen tank design featuring bonded and cocured joining profiles to reinforce the bonding between tank halves, eliminating the need for rivets and ensuring a secure, hydrogen-tight vessel that meets airworthiness regulations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If bonding or co-bonding process is used to join different parts of the hydrogen tank, then the tank can be assembled without rivets (avoiding hydrogen leakage), but debonding failures may occur under flight loads
Solution Approach 1:
The patent employs composite material structures including CFRP (carbon fiber reinforced polymer) tanks with integrated bonding layers and joining profiles. The bonding system combines multiple materials (CFRP, bonding layers, joining profiles) to create a joint that maintains hydrogen tightness while withstanding flight loads through the composite structure's inherent strength properties
Solution Approach 2:
The tank is divided into separate parts (first and second parts) that are joined through bonding/co-bonding processes. This segmentation allows for assembly without rivets (maintaining hydrogen tightness) while the bonding interface is designed with joining profiles to distribute loads and prevent debonding failures
2Adaptability or versatility
If the tank is designed as a single integrated vessel, then bonding failures are minimized, but the tank cannot accommodate internal systems like anti-sloshing walls or pipes
Solution Approach 1:
The tank is segmented into multiple parts that can be assembled around internal systems. The bonding interfaces are designed with joining profiles that distribute loads to prevent debonding failures, allowing the tank to accommodate anti-sloshing walls, pipes, and sensors while maintaining structural integrity and hydrogen tightness
Solution Approach 2:
The patent introduces joining profiles that extend into additional spatial dimensions at the bonding interfaces. These profiles provide load distribution pathways in multiple directions, enhancing bonding reliability while allowing internal systems to be integrated within the tank volume
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The design ensures safe and reliable operation by preventing debonding failures, allowing integration into aircraft systems while adhering to stringent certification standards.
Implementation Method 1
at least one bonding layer (4) laid on at least one joining area (2b, 3b) of one of the halves of the tank (2, 3) to perform their bonding
Implementation Method 2
at least one joining profile (6) cocured or cobonded at the joining area (2b, 3b) of at least one of the halves of the tank (2, 3) to reinforce their bonding
Data Source
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AI summary
The invention refers to a composite hydrogen tank (1) for an aircraft, comprising first and second halves (2, 3) of a tank, each half (2, 3) having an elongated tubular shape with an open end (2a, 3a) and a joining area (2b, 3b) comprising the open end (2a, 3a); at least one bonding layer (4) laid on at least one joining area (2b, 3b) of one of the halves of the tank (2, 3) to perform their bonding; and a joint (5) formed by the bonding of the first and second halves (2, 3) at their open ends (2b, 3b). The joint (5) further comprises at least one joining profile (6) cocured or cobonded at the joining area (2b, 3b) of at least one of the halves of the tank (2, 3) to reinforce their bonding.